Designing turbines for low flow Rankine Cycle for steam is challenging due to their small size, manufacturing restrictions, clearances and cost constraints. Such turbines operate at significant pressure ratios that require use of partial admission and are likely to operate in choked supersonic flow mode due to reduced stage count (controlled by cost).

 

In such designs  it is expected to have relatively low efficiency and a high sensitivity to manufacturing and cost constraints. It also makes overall cycle parameters dependent on the achievable turbine performance, which drives the need in early coupled considerations of the cycle and preliminary turbine design in the search of the best overall solution.

 

Using preliminary design tools which include optimization, such as the ones found in Concepts NREC’s Agile Engineering Design System®, can help solve these problems.

 

Let’s consider, as an example, a design task to find specifications for the most efficient simple Rankine power cycle with a Curtis Stage turbine, with the required electrical power output of 1.5 kW.

 

 

 

 

The problem formulation is as follows:

  • Find preliminary geometry of a Curtis Stage Turbine for a steam Rankine Cycle with the specified electrical power output, optimized for electrical efficiency of the cycle. The requested outcomes are cycle parameters (P, T, mass flow), turbine speed and 1D geometry of the turbine. Pressure in the condenser is fixed, set by level of the rejected heat temperature potential in environment.
  • Constraints are set to follow common design practice for turbines along with aerodynamic, structural and manufacturing limiting conditions.

Modeling of the cycle, coupled with preliminary design of the turbine is set in a simplified way to replicate Rankine Cycle balances (flow, energy) in boiler, pump and turbine components, accounting for pressure loss in piping between pump and turbine, electrical generator electromechanical efficiency with evaluation of cycle electric efficiency. Cycle model includes function to automatically adjust inlet mass flow to deliver target electric power for the current turbine performance iteration.

 

Turbine model in Axial™  is set as a Curtis Stage turbine in redesign mode, that accepts inputs for stage radius, blade angles, admission(s), Laval nozzle area expansion ratio, rotor blades reactions, and pressure at exit of the 1st rotor - to calculate flow path dimensions for provided mass flow;  inlet pressure and temperature, rotation speed - to construct flow path dimensions and calculate performance.

 

Constraints on the turbine design were imposed on aero performance (Zweifel coefficient, permissible flow diffusion at hub in rotor blades, hub reactions in rotors,), structural (AN2, maximum disk rim speed), manufacturing (limiting nozzle angles from extreme tangential values, minimum allowed blade height, minimum allowed throat blade separation distance).

 

The reasonable assumptions needed the cycle calculations forth following parameters:

             Generator electromechanical efficiency

                                Boiler efficiency                                                               

                                Pressure loss between pump and Turbine            

                                Pump efficiency

 

TurboOPT™, with an internal optimizer, is used to set and drive optimization. Simulated annealing followed by the Powel Method were used to execute the optimization.

 

The optimization problem includes 22 input variables (cycle and turbine design parameters), one objective for cycle electric efficiency (the second objective, electric power, is resolved by adjusting cycle mass flow automatically), and 14 constraints.

 

Adopted ranges for the turbine and some of the constraints:

Mass flow range:                                              TBD from optimization

Inlet pressure range:                                       TBD, < 20 Bar

Inlet temperature:                                            TBD, < 450°C

Partial admission:                                             0.1 – 1.0

Rotation speed:                                                 XXXXX-XXXXXX RPM

Electric power:                                                   1500 W

Max Zweifel numbers:                                      <1.2

W2/W1 at hub of the rotors:                            >0.7

Rotor reactions (pressure)                               0.02 – 0.07 (R1), 0.02 – 0.5 (R2)

Max Blade angles:                                             <80° by magnitude

Exit swirl:                                                             -30 – 0°

Allowed range Laval nozzle area ratios:        0.6-1.0

Allowed blade heights:                                     - per available manufacturing

Blade – casing clearances:                               - per available manufacturing

Minimum blade separation distance:           - per available manufacturing

Stage RMS radius:                                             0.01-0.025 m

 

The flowchart of the optimization process and optimized solution is shown below:

 

 

Additional outputs from cycle model for the optimized solution:

 

Turbine aero power, kW                               1.73

Turbine inlet mass flow, kg/sec                  - per optimization result

Pump exit pressure, Bar                                - per optimization result

Turbine inlet pressure, Bar                           - per optimization result

Temperature, °C                                               - per optimization result

Electrical power, kW                                       1.50

R-Cycle ETA electric                                         0.10

 

The optimized geometry of the Curtis Stage meets all manufacturing, aero and structural constraints with the following features:

  • Supersonic (Laval) nozzle with exit Ma ~1.65, with nozzle throat/exit area ~0.68 for fully expanded supersonic mode of operation
  • Choked flow is observed in all nozzle and blade rows (due to pressure ratio PRts >20 in low cost design with 4 blade rows)
  • Partial admission is of order 0.445 (to keep acceptable blade height and deliver best turbine and cycle efficiency)
  • “Customized” vs. conventional Curtis stage geometry and aero traits, to achieve the best tradeoff between performance and meeting manufacturing constraints (especially in 2 front blade rows)

It follows from the review of the optimization history plots and final solution, that most critical constraints, that affect the optimized solution in this example are:

  • Minimum allowed Blade height (first blade rows)
  • Zweifel number in stators (in 2nd stator)

With the obtained results in preliminary geometry, the optimized turbine design can be advanced into AxCent™ for further 3D design and optimization.  The unrefined 3D geometry, generated in AxCent directly from Axial, is visualized below (full admission view) and checked using 3D CFD:

 

 

The results demonstrate how the optimization process can be applied to the coupled consideration of cycle and turbine preliminary design, which delivers not only parameters for the best achievable cycle efficiency, constrained by turbine performance, but also produces turbine geometry and specifications, ready to be advanced into 3D design cycle.